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EPPLER 397 AIRFOIL (e397-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 397 AIRFOIL (e397-il)
Reynolds number: 100,000
Max Cl/Cd: 53.4 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e397-il-100000-n5.txt
Download as CSV file: xf-e397-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 397 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3716   0.05654   0.05145  -0.1118   0.9396   0.0239
  -9.750  -0.3824   0.04837   0.04298  -0.1230   0.9292   0.0238
  -9.500  -0.3864   0.04245   0.03667  -0.1312   0.9163   0.0241
  -9.250  -0.3767   0.03968   0.03373  -0.1338   0.9075   0.0248
  -9.000  -0.3583   0.03696   0.03076  -0.1372   0.9016   0.0263
  -8.750  -0.3432   0.03438   0.02777  -0.1391   0.8944   0.0287
  -8.500  -0.3222   0.03247   0.02569  -0.1408   0.8884   0.0314
  -8.250  -0.2943   0.03041   0.02328  -0.1433   0.8848   0.0353
  -8.000  -0.2766   0.02917   0.02193  -0.1432   0.8774   0.0389
  -7.750  -0.2498   0.02771   0.02013  -0.1446   0.8728   0.0448
  -7.500  -0.2191   0.02649   0.01881  -0.1465   0.8697   0.0515
  -7.250  -0.1986   0.02559   0.01778  -0.1463   0.8630   0.0577
  -7.000  -0.1708   0.02461   0.01659  -0.1471   0.8584   0.0660
  -6.750  -0.1393   0.02373   0.01556  -0.1487   0.8552   0.0759
  -6.500  -0.1143   0.02307   0.01484  -0.1489   0.8502   0.0852
  -6.250  -0.0888   0.02246   0.01413  -0.1491   0.8449   0.0957
  -6.000  -0.0580   0.02180   0.01337  -0.1502   0.8413   0.1085
  -5.750  -0.0249   0.02118   0.01263  -0.1517   0.8386   0.1230
  -5.500  -0.0041   0.02093   0.01232  -0.1509   0.8322   0.1362
  -5.250   0.0247   0.02054   0.01187  -0.1515   0.8281   0.1522
  -5.000   0.0566   0.02013   0.01139  -0.1526   0.8250   0.1703
  -4.750   0.0848   0.01987   0.01105  -0.1530   0.8210   0.1886
  -4.500   0.1087   0.01974   0.01088  -0.1526   0.8156   0.2062
  -4.250   0.1384   0.01952   0.01062  -0.1532   0.8120   0.2259
  -4.000   0.1705   0.01927   0.01031  -0.1541   0.8091   0.2463
  -3.750   0.1951   0.01923   0.01024  -0.1538   0.8043   0.2650
  -3.500   0.2207   0.01920   0.01016  -0.1536   0.7995   0.2845
  -3.250   0.2506   0.01906   0.00999  -0.1541   0.7962   0.3043
  -3.000   0.2827   0.01890   0.00979  -0.1550   0.7935   0.3251
  -2.750   0.3049   0.01900   0.00989  -0.1542   0.7882   0.3432
  -2.500   0.3309   0.01902   0.00987  -0.1540   0.7837   0.3630
  -2.250   0.3608   0.01893   0.00978  -0.1545   0.7805   0.3833
  -2.000   0.3928   0.01880   0.00964  -0.1552   0.7780   0.4044
  -1.750   0.4126   0.01902   0.00988  -0.1540   0.7723   0.4230
  -1.500   0.4386   0.01907   0.00993  -0.1538   0.7680   0.4440
  -1.250   0.4684   0.01901   0.00990  -0.1542   0.7649   0.4656
  -1.000   0.5004   0.01892   0.00979  -0.1549   0.7625   0.4895
  -0.750   0.5179   0.01924   0.01019  -0.1533   0.7563   0.5098
  -0.500   0.5439   0.01930   0.01031  -0.1530   0.7523   0.5335
  -0.250   0.5739   0.01926   0.01029  -0.1533   0.7493   0.5596
   0.000   0.6048   0.01920   0.01026  -0.1538   0.7467   0.5874
   0.250   0.6198   0.01961   0.01079  -0.1517   0.7401   0.6117
   0.500   0.6462   0.01966   0.01090  -0.1514   0.7362   0.6408
   0.750   0.6758   0.01960   0.01090  -0.1515   0.7334   0.6727
   1.000   0.6967   0.01981   0.01120  -0.1502   0.7288   0.7044
   1.250   0.7145   0.02005   0.01156  -0.1484   0.7232   0.7384
   1.500   0.7391   0.02001   0.01162  -0.1474   0.7198   0.7783
   1.750   0.7648   0.01984   0.01152  -0.1465   0.7172   0.8257
   2.000   0.7702   0.02022   0.01207  -0.1423   0.7099   0.8935
   2.250   0.8003   0.02024   0.01211  -0.1429   0.7057   1.0000
   2.500   0.8352   0.02024   0.01204  -0.1443   0.7028   1.0000
   2.750   0.8545   0.02076   0.01256  -0.1432   0.6967   1.0000
   3.000   0.8797   0.02104   0.01283  -0.1431   0.6915   1.0000
   3.250   0.9134   0.02104   0.01281  -0.1441   0.6882   1.0000
   3.500   0.9343   0.02146   0.01325  -0.1432   0.6822   1.0000
   3.750   0.9574   0.02177   0.01358  -0.1426   0.6763   1.0000
   4.000   0.9918   0.02169   0.01351  -0.1437   0.6728   1.0000
   4.250   1.0077   0.02224   0.01412  -0.1419   0.6654   1.0000
   4.500   1.0351   0.02235   0.01426  -0.1419   0.6599   1.0000
   4.750   1.0725   0.02211   0.01404  -0.1433   0.6563   1.0000
   5.000   1.0810   0.02283   0.01486  -0.1403   0.6469   1.0000
   5.250   1.1164   0.02259   0.01466  -0.1414   0.6422   1.0000
   5.500   1.1280   0.02318   0.01535  -0.1389   0.6331   1.0000
   5.750   1.1616   0.02295   0.01517  -0.1395   0.6274   1.0000
   6.000   1.1734   0.02346   0.01578  -0.1370   0.6177   1.0000
   6.250   1.2095   0.02308   0.01546  -0.1380   0.6113   1.0000
   6.500   1.2161   0.02366   0.01615  -0.1346   0.6003   1.0000
   6.750   1.2345   0.02384   0.01641  -0.1329   0.5907   1.0000
   7.000   1.2629   0.02365   0.01628  -0.1326   0.5814   1.0000
   7.250   1.2714   0.02412   0.01686  -0.1294   0.5684   1.0000
   7.500   1.2847   0.02439   0.01720  -0.1269   0.5539   1.0000
   7.750   1.3001   0.02460   0.01745  -0.1248   0.5378   1.0000
   8.000   1.3141   0.02491   0.01779  -0.1225   0.5199   1.0000
   8.250   1.3223   0.02557   0.01851  -0.1197   0.5005   1.0000
   8.500   1.3350   0.02610   0.01907  -0.1174   0.4802   1.0000
   8.750   1.3480   0.02669   0.01965  -0.1153   0.4588   1.0000
   9.000   1.3578   0.02751   0.02046  -0.1130   0.4351   1.0000
   9.250   1.3668   0.02845   0.02135  -0.1106   0.4097   1.0000
   9.500   1.3741   0.02956   0.02237  -0.1082   0.3837   1.0000
   9.750   1.3786   0.03093   0.02367  -0.1056   0.3571   1.0000
  10.000   1.3819   0.03247   0.02514  -0.1032   0.3313   1.0000
  10.250   1.3840   0.03420   0.02679  -0.1008   0.3064   1.0000
  10.500   1.3851   0.03607   0.02859  -0.0985   0.2824   1.0000
  10.750   1.3855   0.03811   0.03056  -0.0964   0.2582   1.0000
  11.000   1.3857   0.04026   0.03264  -0.0944   0.2367   1.0000
  11.250   1.3869   0.04242   0.03479  -0.0926   0.2158   1.0000
  11.500   1.3871   0.04475   0.03708  -0.0910   0.1959   1.0000
  11.750   1.3862   0.04728   0.03958  -0.0894   0.1760   1.0000
  12.000   1.3850   0.04994   0.04219  -0.0880   0.1548   1.0000
  12.250   1.3823   0.05286   0.04503  -0.0868   0.1353   1.0000
  12.500   1.3812   0.05574   0.04787  -0.0857   0.1164   1.0000
  12.750   1.3795   0.05877   0.05087  -0.0848   0.1009   1.0000
  13.000   1.3785   0.06184   0.05393  -0.0840   0.0884   1.0000
  13.250   1.3780   0.06494   0.05705  -0.0834   0.0782   1.0000
  13.500   1.3768   0.06819   0.06032  -0.0829   0.0700   1.0000
  13.750   1.3770   0.07137   0.06357  -0.0825   0.0629   1.0000
  14.000   1.3753   0.07486   0.06712  -0.0823   0.0575   1.0000
  14.250   1.3732   0.07849   0.07083  -0.0822   0.0528   1.0000
  14.500   1.3687   0.08251   0.07487  -0.0823   0.0491   1.0000
  14.750   1.3677   0.08613   0.07866  -0.0825   0.0449   1.0000
  15.000   1.3635   0.09027   0.08287  -0.0828   0.0418   1.0000
  15.250   1.3611   0.09420   0.08691  -0.0832   0.0386   1.0000
  15.500   1.3603   0.09800   0.09088  -0.0838   0.0353   1.0000
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